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MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 82 13.31% (mh82-il)
Reynolds number: 500,000
Max Cl/Cd: 90.49 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh82-il-500000-n5.txt
Download as CSV file: xf-mh82-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 82  13.31%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4076   0.08589   0.08256   0.0025   0.5930   0.0094
  -8.500  -0.4031   0.08310   0.07976   0.0009   0.5836   0.0089
  -8.000  -0.5668   0.03379   0.02945  -0.0256   0.6074   0.0074
  -7.500  -0.5391   0.02748   0.02226  -0.0248   0.5874   0.0073
  -7.250  -0.5202   0.02521   0.01962  -0.0242   0.5768   0.0073
  -7.000  -0.4989   0.02335   0.01743  -0.0236   0.5665   0.0073
  -6.750  -0.4761   0.02181   0.01559  -0.0231   0.5561   0.0073
  -6.500  -0.4522   0.02044   0.01396  -0.0226   0.5457   0.0073
  -6.250  -0.4276   0.01923   0.01251  -0.0221   0.5357   0.0074
  -6.000  -0.4025   0.01811   0.01117  -0.0216   0.5255   0.0074
  -5.750  -0.3767   0.01721   0.01011  -0.0212   0.5160   0.0075
  -5.500  -0.3504   0.01644   0.00919  -0.0208   0.5060   0.0076
  -5.250  -0.3238   0.01577   0.00841  -0.0205   0.4966   0.0077
  -5.000  -0.2969   0.01521   0.00773  -0.0202   0.4875   0.0078
  -4.750  -0.2697   0.01469   0.00713  -0.0198   0.4780   0.0079
  -4.500  -0.2424   0.01424   0.00657  -0.0195   0.4691   0.0081
  -4.250  -0.2149   0.01381   0.00606  -0.0193   0.4606   0.0083
  -4.000  -0.1873   0.01342   0.00559  -0.0190   0.4525   0.0086
  -3.750  -0.1595   0.01306   0.00515  -0.0187   0.4438   0.0088
  -3.500  -0.1316   0.01275   0.00475  -0.0185   0.4357   0.0093
  -3.250  -0.1035   0.01248   0.00441  -0.0183   0.4274   0.0096
  -3.000  -0.0756   0.01218   0.00404  -0.0181   0.4202   0.0103
  -2.750  -0.0473   0.01196   0.00378  -0.0179   0.4131   0.0111
  -2.500  -0.0190   0.01179   0.00353  -0.0177   0.4056   0.0121
  -2.250   0.0094   0.01159   0.00330  -0.0176   0.3984   0.0137
  -2.000   0.0377   0.01144   0.00310  -0.0174   0.3907   0.0163
  -1.750   0.0661   0.01127   0.00292  -0.0173   0.3842   0.0227
  -1.500   0.0942   0.01105   0.00276  -0.0172   0.3777   0.0406
  -1.250   0.1220   0.01080   0.00263  -0.0171   0.3716   0.0797
  -1.000   0.1501   0.01059   0.00256  -0.0170   0.3658   0.1214
  -0.750   0.1782   0.01042   0.00249  -0.0170   0.3592   0.1648
  -0.500   0.2058   0.01014   0.00244  -0.0169   0.3534   0.2392
  -0.250   0.2330   0.00981   0.00240  -0.0169   0.3475   0.3389
   0.000   0.2598   0.00946   0.00238  -0.0167   0.3421   0.4544
   0.250   0.2862   0.00912   0.00238  -0.0164   0.3374   0.5707
   0.500   0.3115   0.00877   0.00240  -0.0157   0.3326   0.6898
   0.750   0.3350   0.00850   0.00247  -0.0144   0.3274   0.8061
   1.000   0.3594   0.00845   0.00255  -0.0132   0.3227   0.8770
   1.250   0.3867   0.00848   0.00261  -0.0125   0.3180   0.9161
   1.500   0.4167   0.00856   0.00265  -0.0126   0.3132   0.9420
   1.750   0.4502   0.00868   0.00270  -0.0135   0.3087   0.9606
   2.000   0.4904   0.00877   0.00274  -0.0159   0.3046   0.9791
   2.250   0.5343   0.00887   0.00278  -0.0190   0.2995   0.9921
   2.500   0.5770   0.00901   0.00283  -0.0221   0.2945   1.0000
   2.750   0.6025   0.00913   0.00291  -0.0215   0.2911   1.0000
   3.000   0.6282   0.00924   0.00299  -0.0210   0.2879   1.0000
   3.250   0.6540   0.00937   0.00307  -0.0205   0.2846   1.0000
   3.500   0.6798   0.00952   0.00318  -0.0201   0.2810   1.0000
   3.750   0.7055   0.00970   0.00330  -0.0197   0.2775   1.0000
   4.000   0.7319   0.00982   0.00341  -0.0193   0.2746   1.0000
   4.250   0.7583   0.00996   0.00353  -0.0190   0.2717   1.0000
   4.500   0.7849   0.01012   0.00366  -0.0187   0.2687   1.0000
   4.750   0.8114   0.01030   0.00381  -0.0185   0.2656   1.0000
   5.000   0.8379   0.01050   0.00397  -0.0182   0.2625   1.0000
   5.250   0.8650   0.01064   0.00412  -0.0181   0.2600   1.0000
   5.500   0.8920   0.01080   0.00428  -0.0179   0.2573   1.0000
   5.750   0.9189   0.01098   0.00445  -0.0178   0.2546   1.0000
   6.000   0.9457   0.01118   0.00464  -0.0177   0.2517   1.0000
   6.250   0.9723   0.01141   0.00485  -0.0175   0.2488   1.0000
   6.500   0.9992   0.01161   0.00505  -0.0175   0.2464   1.0000
   6.750   1.0262   0.01179   0.00525  -0.0174   0.2441   1.0000
   7.000   1.0530   0.01198   0.00547  -0.0173   0.2416   1.0000
   7.250   1.0796   0.01220   0.00569  -0.0172   0.2388   1.0000
   7.500   1.1059   0.01245   0.00594  -0.0171   0.2360   1.0000
   7.750   1.1319   0.01274   0.00621  -0.0170   0.2334   1.0000
   8.000   1.1586   0.01293   0.00645  -0.0170   0.2314   1.0000
   8.250   1.1851   0.01315   0.00671  -0.0169   0.2291   1.0000
   8.500   1.2112   0.01340   0.00698  -0.0168   0.2263   1.0000
   8.750   1.2370   0.01367   0.00727  -0.0167   0.2236   1.0000
   9.000   1.2622   0.01398   0.00759  -0.0166   0.2209   1.0000
   9.250   1.2874   0.01428   0.00792  -0.0164   0.2187   1.0000
   9.500   1.3132   0.01453   0.00823  -0.0163   0.2164   1.0000
   9.750   1.3384   0.01481   0.00856  -0.0162   0.2136   1.0000
  10.000   1.3631   0.01512   0.00890  -0.0160   0.2109   1.0000
  10.250   1.3871   0.01548   0.00929  -0.0158   0.2081   1.0000
  10.500   1.4106   0.01587   0.00970  -0.0155   0.2053   1.0000
  10.750   1.4349   0.01617   0.01007  -0.0153   0.2028   1.0000
  11.000   1.4584   0.01651   0.01048  -0.0151   0.1998   1.0000
  11.250   1.4809   0.01691   0.01092  -0.0147   0.1966   1.0000
  11.500   1.5020   0.01739   0.01142  -0.0143   0.1936   1.0000
  11.750   1.5236   0.01781   0.01190  -0.0138   0.1908   1.0000
  12.000   1.5447   0.01823   0.01240  -0.0134   0.1877   1.0000
  12.250   1.5640   0.01874   0.01296  -0.0127   0.1842   1.0000
  12.500   1.5806   0.01936   0.01361  -0.0119   0.1810   1.0000
  12.750   1.5962   0.01996   0.01428  -0.0109   0.1781   1.0000
  13.000   1.6084   0.02060   0.01500  -0.0094   0.1752   1.0000
  13.250   1.6175   0.02147   0.01594  -0.0080   0.1719   1.0000
  13.500   1.6242   0.02264   0.01715  -0.0069   0.1688   1.0000
  13.750   1.6322   0.02389   0.01847  -0.0062   0.1659   1.0000
  14.000   1.6414   0.02517   0.01983  -0.0057   0.1623   1.0000
  14.250   1.6474   0.02679   0.02153  -0.0054   0.1590   1.0000
  14.500   1.6491   0.02889   0.02367  -0.0052   0.1557   1.0000
  14.750   1.6545   0.03075   0.02563  -0.0052   0.1527   1.0000
  15.000   1.6576   0.03291   0.02787  -0.0053   0.1492   1.0000
  15.250   1.6547   0.03573   0.03074  -0.0056   0.1454   1.0000
  15.500   1.6502   0.03879   0.03387  -0.0061   0.1420   1.0000
  15.750   1.6483   0.04165   0.03683  -0.0066   0.1384   1.0000
  16.000   1.6392   0.04537   0.04061  -0.0074   0.1344   1.0000
  16.250   1.6259   0.04966   0.04497  -0.0085   0.1312   1.0000
  16.500   1.6183   0.05336   0.04877  -0.0095   0.1274   1.0000
  16.750   1.6041   0.05809   0.05357  -0.0110   0.1234   1.0000
  17.000   1.5858   0.06348   0.05902  -0.0128   0.1200   1.0000
  17.250   1.5746   0.06811   0.06374  -0.0145   0.1159   1.0000
  17.500   1.5571   0.07373   0.06942  -0.0167   0.1118   1.0000
  17.750   1.5385   0.07963   0.07540  -0.0190   0.1083   1.0000
  18.000   1.5234   0.08520   0.08104  -0.0213   0.1040   1.0000
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